# DATA FOR King Air C90GT
# Collected from AOPA Pilot article
# and rough photogrammetry
from __future__ import division

data = dict()
ac = dict()
# ==AERO==================================
aero = dict()
aero['CLmax_TO']   = {'value' : 1.52}

polar = dict()
polar['e']              = {'value' : 0.80}
polar['CD0_TO']         = {'value' : 0.040}
polar['CD0_cruise']     = {'value' : 0.022}

aero['polar'] = polar
ac['aero'] = aero

# ==GEOMETRY==============================
geom = dict()
wing = dict()
wing['S_ref']           = {'value': 27.308, 'units': 'm**2'}
wing['AR']              = {'value': 8.5834}
wing['c4sweep']         = {'value': 1.0, 'units': 'deg'}
wing['taper']           = {'value': 0.397}
wing['toverc']          = {'value': 0.19}
geom['wing'] = wing

fuselage = dict()
fuselage['S_wet']       = {'value': 41.3, 'units': 'm**2'}
fuselage['width']       = {'value': 1.6, 'units': 'm'}
fuselage['length']      = {'value': 10.79, 'units': 'm'}
fuselage['height']      = {'value': 1.9, 'units': 'm'}
geom['fuselage'] = fuselage

hstab = dict()
hstab['S_ref']          = {'value': 8.08, 'units': 'm**2'}
hstab['c4_to_wing_c4']  = {'value': 5.33, 'units': 'm'}
geom['hstab'] = hstab

vstab = dict()
vstab['S_ref']          = {'value': 3.4, 'units': 'm**2'}
geom['vstab'] = vstab

nosegear = dict()
nosegear['length'] = {'value': 0.95, 'units': 'm'}
geom['nosegear'] = nosegear

maingear = dict()
maingear['length'] = {'value': 0.88, 'units': 'm'}
geom['maingear'] = maingear

ac['geom'] = geom

# ==WEIGHTS========================
weights = dict()
weights['MTOW']         = {'value': 4581, 'units': 'kg'}
weights['W_fuel_max']   = {'value': 1166, 'units': 'kg'}
weights['MLW']          = {'value': 4355, 'units': 'kg'}
weights['W_battery']    = {'value': 100, 'units': 'kg'}

ac['weights'] = weights

# ==PROPULSION=====================
propulsion = dict()
engine = dict()
engine['rating']        = {'value': 750, 'units': 'hp'}
propulsion['engine']    = engine

propeller = dict()
propeller['diameter']     = {'value': 2.28, 'units': 'm'}
propulsion['propeller'] = propeller

motor = dict()
motor['rating']         = {'value': 527.2, 'units': 'hp'}
propulsion['motor'] = motor

generator = dict()
generator['rating']         = {'value': 1083.7, 'units': 'hp'}
propulsion['generator'] = generator

ac['propulsion'] = propulsion

# Some additional parameters needed by the empirical weights tools
ac['num_passengers_max'] = {'value': 8}
ac['q_cruise'] = {'value': 98, 'units': 'lb*ft**-2'}
ac['num_engines'] = {'value': 2}
data['ac'] = ac